# TCDS A23NM: Buehn Dennis G.

- Type: Type certificate data sheet
- Status: Current
- Holder: Buehn Dennis G.
- Revision: 4
- Revised: September 10, 1998
- Product: Aircraft, Large Airplane
- Certification basis: Part 21
- Data sheet PDF: https://openairdocs.org/files/sha256/d0/4d/d04d68bb2a2a075b788fd12a6757d1068da06e9b203fa7ca6c01dd5797c7f76c
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/B32054078F002CDE86256D1D005E4D1E.0001
- Page: https://openairdocs.org/tcds/A23NM

## Models (3)

As the data sheet lists them.

- SA-16A (UF-1)
- HU-16C (UF-1)
- TC-16C (UF-1T)

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
P a g e  N o . 12345678
R e v .  N o . 43344344
FEDERAL AVIATION ADMINISTRATION
A23NM
Revision 4
BUEHN
HU-16C (UF-1)
TU-16C (UF-1T)
SA-16A (UF-1)
September 10, 1998 
TYPE CERTIFICATE DATA SHEET NO. A23NM 
This data sheet, which is a part of Type Certificate No. A23NM, prescribes conditions and limitations under which the product
for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.
Type Certificate Holder Dennis G. Buehn
2600 Graves #33
Carson City, Nevada   89706
I -   Model HU-16C (UF-1) (Navy), (Restricted Category), Approved August 17, 1988
Model TU-16C (UF-1T) (Navy Trainer) (Restricted Category), Approved December 23, 1988 (See Note 12)
Engine (2) Wright R-1820-76A, B, C or D, Single Stage, Two Speed Engines, Geared 3 to 2
Reduction Gearing
Fuel 100/130 or 100 LL Grade Aviation Fuel
Engine Limits
(Per AN 01-85-AB-1) Power Setting RPM
  MP
In. Hg. Mixture
 
BHP
Take-off (30 min.) 2700 51.5 Rich 1425
Military 2700 50.5 Normal 1425
Normal Rated (Max. Cont.) 2500 46.5 Normal 1275
High Cruise 2250 37.0 Normal 950
Propellers Hamilton Standard Matched Hubs and Propellers
Hub Designation Applicable Propellers*
43D50-601 6601A-7 thru -9, 6621A-7, 6621B-7, 6999-7 thru -9, 7005-7,
7007B, 7007B-7
43D50-603 6601A-7 thru -9, 6601B-7, 6621A-7,  6999-7 thru -9, 7005-7,
7007B, 7007B-7
43D50-605 6621B-7
43D50-609 7001B-7, 7003B-7, 7007B-7
43D50-613 7001B-7, 7003B-7, 7007B-7
43D50-615 7007C-7
43D50-637 6601A-7 thru -9, 6621A-7,  6999-7 thru -9, 7005-7, 7007B,
7007B-7, 7007F-7
43D50-639 7007E-7, 7007F-7
43D50-641 7001C-7, 7003C-7
*Propellers must be used in matched sets on each hub
Diameter 11 feet
Pitch settings:  Low  (fine) 16°, High (feathered) 89°, Reverse -12°

A23NM
Page 2 of 8
Airspeed Limits Maximum permissible indicated airspeeds are as follows per AN 01-85AB-1 Flight
Handbook:
Smooth Air 260 Knots
Flaps 15° 175 Knots
Flaps 30° 135 Knots
Flaps 45° 115 Knots
Gear Down 130 Knots
Landing Lights Down 120 Knots
Full Aileron Deflection 175 Knots
Severe Turbulence 110-130 Knots
C. G. Range +20.5 MAC to +28.0 MAC
Datum See T. O. 1-1B-40 (AN 01-1B-40) Chart E with Dennis Buehn Cargo Tie-Down
Appendix.
Field Take-off Weight 33,500 lbs.
Field Landing Weight 29,500 lbs.
Water Take-off & Landing 29,500 lbs.
Leveling Means See AN-01-1B-40, Chart E
Minimum Crew Two (Pilot and Co-Pilot)
Cargo Capacity See T. O. 1-1B-40, Chart E
Fuel Capacity 675 gals. (2) Main Tanks
414.5 gals. (2) Float Tanks
150 or 300 gals. (2 ea.) Auxiliary Tanks
Oil Capacity 58 gals. (2) Nacelle at 29 gals. each
Settings & Ranges of
 Movement of Control
 Surfaces and Flaps
(Per 01-85AB-2, Section 1)
 Movements Tolerances
Degrees Inches Degrees Inches
Ailerons Up (from Neutral) 17 6½ ±1 ±3/16
Down (from Neutral) 17 6½ ±1 ±3/16
Elevators Up (from streamline
with stabilizer) 30 15 ±1 ±3/16
Down (from streamline 
with stabilizer) 20 10-1/16 ±1 ±3/16
Rudder Right (from streamline 
with fin) 20 ±1 ±3/16
Left (from streamline 
with fin) 15 ±1 ±3/16
Flaps Up (measured at
inboard end)
0
15
0
12-1/32
-
±3
±3/32
±2-13/32
Full 30 24-2/32 ±3 ±2-13/32
Down 40 32-1/32 ±3 ±2-13/32

A23NM
Page 3 of 8
Settings & Ranges of
 Movement of Control
 Surfaces and Flaps (Continued)
(Per 01-85AB-2, Section 1)
 Movements Tolerances
Degrees Inches Degrees Inches
Trim Tabs
    Elevator Up (from elevator
trailing edge)
Down  (from elevator
trailing edge)
5
12
23/32
1-21/32
±1
±1
±1/8
±1/8
    Rudder Right  (from rudder
trailing edge)
Left (from rudder trailing
edge)
17
25
3-5/16
4-27/32
±1
±1
±3/16
±3/16
    Aileron Up (from aileron
trailing edge)
Down (from aileron
trailing edge)
18
12
1-5/8
1-1/16
±1
±1
±3/32
±3/32
Serial Nos. Eligible Model HU-16C (UF-1) (Navy)
Factory Number Bureau Number
10 124374
16 124376
19 124377
22 124378
25 124379
90 149836 (Ex 51-17)
233 131890
236 131891
239 131892
242 131893
245 131894
249 131895
252 131896
254 131897
257 131898
261 131899
264 131900
269 131902
273 131903
278 131905
281 131906
284 131907
290 131909
293 131910
296 131911
311 131916
333 131904
338 131908
367 1290* (142360)
368 1291* (142361)
369 1292* (142362)
373 137900

A23NM
Page 4 of 8
Serial Nos. Eligible (cont’d) Model HU-16C (UF-1) (Navy)
Factory Number Bureau Number
375 137902
378 137905
381 137908
382 137909
385 137912
388 137905
389 137916
396 137923
397 137924
398 137925
399 137926
400 137927
401 137928
402 137929
403 137930
405 137932
406 137933
409 141262
412 141265
414 141267
418 141271
420 141273
423 141276
424 141277
*Previously UF-1CG (Coast Guard)
Model TU-16C (UF-1T)
305 131914
308 131915
311 131916
314 131917
320 131918
Certification Basis Type Certificate A23NM, issued August 17, 1988, for the special purpose of carriage of
cargo.  Reference to Advisory Circular 21.17, dated March 14, 1982, specifies that
carriage of cargo is considered a special purpose under FAR 21.25(b)(7).  Date of
application December 8, 1986.  The modifications incorporated are considered
appropriate to the special purpose operation.  The criteria established in Civil
Regulations Part 4b appropriate to the special purpose operation has been used to
evaluate these particular changes and demonstrate that the original level of airworthiness
established by the military requirements has not been reduced.  A Finding of No
Significant Impact (FONSI) for the modified Grumman (Navy) Model HU-16C (UF-1)
aircraft has been accomplished and approved on March 21, 1988.  A finding under the
applicable provisions of the Noise Control Act of 1972 has also been accomplished and
approved on March 21, 1988, for the modified Grumman HU-16C (UF-1) aircraft
(Restricted Category- Military Surplus).
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations
(see Certification Basis) must be installed.  In addition, NAVWEPS Flight Manual
(NAVY), 01-85AB-1, revised April 8, 1965, with Dennis G. Buehn FAA Approved
AFM Supplement No. 1 to NAVWEPS 01-85AB-1 with Dennis Buehn cargo tie down
appendix is required.

A23NM
Page 5 of 8
Date of Application December 8, 1986
Production Basis None.  Prior to original certification, an FAA representative must perform an inspection
for workmanship, material, and conformity with the approved technical data.  Applicable
Technical Orders affecting airworthiness must be accomplished.
II    Model SA-16A (UF-1) (USAF) (Restricted Category), Approved September 10, 1998 (See Note 13)
Engine (2) Wright R-1820-76A, B, C or D, Single Stage, Two Speed Engines, Geared 3 to 2
Reduction Gearing
Fuel 100/130 or 100 LL Grade Aviation Fuel
Engine Limits
(Per AN 01-85-AB-1) Power Setting RPM
  MP
In. Hg. Mixture
 
BHP
Take-off (30 min.) 2700 51.5 Rich 1425
Military 2700 50.5 Normal 1425
Normal Rated (Max. Cont.) 2500 46.5 Normal 1275
High Cruise 2250 37.0 Normal 950
Propellers Hamilton Standard Matched Hubs and Propellers
Hub Designation Applicable Propellers*
43D50-601 6601A-7 thru -9, 6621A-7, 6621B-7, 6999-7 thru -9, 7005-7,
7007B, 7007B-7
43D50-603 6601A-7 thru -9, 6601B-7, 6621A-7,  6999-7 thru -9, 7005-7,
7007B, 7007B-7
43D50-605 6621B-7
43D50-609 7001B-7, 7003B-7, 7007B-7
43D50-613 7001B-7, 7003B-7, 7007B-7
43D50-615 7007C-7
43D50-637 6601A-7 thru -9, 6621A-7,  6999-7 thru -9, 7005-7, 7007B,
7007B-7, 7007F-7
43D50-639 7007E-7, 7007F-7
43D50-641 7001C-7, 7003C-7
*Propellers must be used in matched sets on each hub
Diameter 11 feet
Pitch settings:  Low  (fine) 16°, High (feathered) 89°, Reverse -12°
Airspeed Limits Maximum permissible indicated airspeeds are as follows per AN 01-85AB-1 Flight
Handbook:
Smooth Air 260 Knots
Flaps 15° 175 Knots
Flaps 30° 135 Knots
Flaps 45° 115 Knots
Gear Down 130 Knots
Landing Lights Down 120 Knots
Full Aileron Deflection 175 Knots
Severe Turbulence 110-130 Knots
C. G. Range +20.5 MAC to +28.0 MAC
Datum See T. O. 1U-16 (H)A-5 (USAF) with Dennis Buehn Cargo Tie-Down Appendix.

A23NM
Page 6 of 8
Field Take-off Weight 33,500 lbs.
Field Landing Weight 29,500 lbs.
Water Take-off & Landing 29,500 lbs.
Leveling Means See AN-01-1B-40, Chart E
Minimum Crew Two (Pilot and Co-Pilot)
Cargo Capacity See T. O. 1-1B-40, Chart E
Fuel Capacity 675 gals. (2) Main Tanks
414.5 gals. (2) Float Tanks
150 or 300 gals. (2 ea.) Auxiliary Tanks
Oil Capacity 58 gals. (2) Nacelle at 29 gals. each
Settings & Ranges of
 Movement of Control
 Surfaces and Flaps
(Per 01-85AB-2, Section 1)
 Movements Tolerances
Degrees Inches Degrees Inches
Ailerons Up (from Neutral) 17 6½ ±1 ±3/16
Down (from Neutral) 17 6½ ±1 ±3/16
Elevators Up (from streamline
with stabilizer) 30 15 ±1 ±3/16
Down (from streamline 
with stabilizer) 20 10-1/16 ±1 ±3/16
Rudder Right (from streamline 
with fin) 20 ±1 ±3/16
Left (from streamline 
with fin) 15 ±1 ±3/16
Flaps Up (measured at
inboard end)
0
15
0
12-1/32
-
±3
±3/32
±2-13/32
Full 30 24-2/32 ±3 ±2-13/32
Down 40 32-1/32 ±3 ±2-13/32
Trim Tabs
    Elevator Up (from elevator
trailing edge)
Down  (from elevator
trailing edge)
5
12
23/32
1-21/32
±1
±1
±1/8
±1/8
    Rudder Right  (from rudder
trailing edge)
Left (from rudder trailing
edge)
17
25
3-5/16
4-27/32
±1
±1
±3/16
±3/16
    Aileron Up (from aileron
trailing edge)
Down (from aileron
trailing edge)
18
12
1-5/8
1-1/16
±1
±1
±3/32
±3/32
Serial Nos. Eligible Model SA-16A (UF-1) (USAF)
Factory Number Bureau Number
32 49-074

A23NM
Page 7 of 8
Certification Basis Type Certificate A23NM, issued August 17, 1988, for the special purpose of carriage of
cargo.  Reference to Advisory Circular 21.17, dated March 14, 1982, specifies that
carriage of cargo is considered a special purpose under FAR 21.25(b)(7).  Date of
application December 8, 1986.  The modifications incorporated are considered
appropriate to the special purpose operation.  The criteria established in Civil
Regulations Part 4b appropriate to the special purpose operation has been used to
evaluate these particular changes and demonstrate that the original level of airworthiness
established by the military requirements has not been reduced.  A Finding of No
Significant Impact (FONSI) for the modified Grumman (Navy) Model HU-16C (UF-1)
aircraft has been accomplished and approved on March 21, 1988.  A finding under the
applicable provisions of the Noise Control Act of 1972 has also been accomplished and
approved on March 21, 1988, for the modified Grumman HU-16C (UF-1) aircraft
(Restricted Category- Military Surplus).  These findings also apply to the Grumman
(Navy Trainer) Model TU-16C (UF-1T) and to the Grumman (Air Force) Model SA-16A
(UF-1) aircraft.
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations
(see Certification Basis) must be installed.  In addition, NAVWEPS Flight Manual
(USAF) T.O. 1U-16(H)A-1, revised April 8, 1965, with Dennis G. Buehn FAA
Approved AFM Supplement No. 1 to NAVWEPS 1U-16(H)A-1 with Dennis Buehn
cargo tie down appendix is required.
Date of Application May 27, 1996
Production Basis None.  Prior to original certification, an FAA representative must perform an inspection
for workmanship, material, and conformity with the approved technical data.  Applicable
Technical Orders affecting airworthiness must be accomplished.
NOTES
Note 1 Current weight and balance information, including a list of equipment in certified empty
weight and loading instructions, must be in the airplane at time of original airworthiness
certification and all times thereafter.  Each compartment, respectively, must have a
placard showing the maximum loading weight for that compartment.  Cargo must be
loaded on the airplane in accordance with T.O. 01-18-40, and must be secured using TSO
straps or nets anchored to wedjit tie-down fasteners installed in the airplane.  (See AFM
Supplement No. 1 to NAVWEPS Flight Manual 01-85AB-1 with Dennis Buehn cargo tie
down appendix for compartment loading chart and anchoring instructions.)
Note 2 The initial, minimum scheduled maintenance program requirements for  the UH-16C and
the TU-16C are contained in document DGB 16-2.  This document also applies to the
SA-16A.
A. The airplane must satisfactorily pass an inspection for conformity with 01-85AB-2
(for Models HU-16C and TU-16C) or T.O. 1U-16(H)A-2-1 (for Model SA-16A) for
possible hidden damage and for workmanship and materials used in making any
repairs and/or alterations.
B. The maintenance, overhaul and modification records must be reviewed for changes
made by the military services that may have an effect on the airworthiness of the
airplane.  Modifications and  changes of equipment which affect the safety or
performance of the airplane must be approved by the Federal Aviation
Administration.
C. Conduct an inspection of the engine support structures to verify their structural
integrity.
D. This aircraft is not equipped or approved for operation with JATO system.

A23NM
Page 8 of 8
Note 2 (cont’d) E. This aircraft is not equipped or approved for operation with APU.
F. Engine supercharger high speed ratio (high blower) must be permanently
deactivated for all operations.
G. The modification data plate in restricted category must be installed next to
manufacturer’s data plate in the cockpit.
H. Aircraft must be flight tested and FAA Form 8130-9 completed.
Note 3 Reserved.
Note 4 Carriage of hazar dous materials is prohibited unless compliance is shown with applicable
regulations in the Code of Federal Regulations, Title 49, Part 175.
Note 5 The following note must be placed under "exceptions" on all Export Certificates of
Airworthiness for this airplane.  "This airplane is type certificated in the restricted
category and may not meet the applicable airworthiness code as provided by Annex 8 to
the Convention of International Civil Aviation."
Note 6 Flight into known ic ing conditions is prohibited.
Note 7 Approved cargo nets/straps to be FAA TSO'd equipment.
Note 8 Two (2) oxygen masks providing 100% breathing capacity for both pilots, and two (2)
smoke masks, are required for flight in the aircraft at all times.
Note 9 Two (2) fire extinguishers must be installe d  - one in the cockpit and one in the cabin are
required.
Note 10 This approval applies to this airplane modified in accordance with Drawing No. 
DGB16-1 dated January 12, 1988, or later FAA approved revision.
Note 11 The following placard must be installed in clear view of the pilot:
RESTRICTED CATEGORY
This airplane must be operated as a restricted category airplane and in accordance with
operating limitations stated in NAVWEPS 01-85AB-1 (Navy models) or T.O. 1U-
16(H)A-1 (USAF models), Dennis G. Buehn FAA Approved AFM Supplement No. 1,
and in accordance with all placards and manuals.
No persons may be carried on a restricted category civil aircraft unless they are necessary
for the accomplishment of the work activity directly associated with that special purpose.
Ref. 91.313(d) (formerly 91.39(c)(4)).
Note 12 Navy Trainer Model UF-1T airplanes are identical to the standard Navy UF-1 airplanes
except that they are equipped with additional navigation instruments and extra cabin
equipment.
Note 13 USAF Model SA-16A airplanes are esse ntially identical to the standard Navy UF-1
airplanes.
- END -
```

## ADs

None name its models.

## Registered aircraft by registry model (OpenAirDocs)

- [Grumman SA 16A](https://openairdocs.org/model/grumman-sa-16a): 0 aircraft (registry code 3950404)

## STCs approved under this data sheet (5)

- [STC SA39CH](https://openairdocs.org/stc/SA39CH): Installation of an Amphibian Landing Gear Position Advisory System/Laser Gear Advisory System. Wipaire Inc.
- [STC SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments
- [STC SA00432SE](https://openairdocs.org/stc/SA00432SE): Installation of EGT 701 series fuel flow instrument.. J P Instruments
- [STC SA00861SE](https://openairdocs.org/stc/SA00861SE): Installation of J.P. Instruments (JPI) fuel flow indicating system. J P Instruments
- [STC SA02153LA-D](https://openairdocs.org/stc/SA02153LA-D) (historical): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc

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